Cooling System for Aerospace Vehicle Components
AssigneeThe Boeing Company
InventorDavid E. Blanding
Life of this patent
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Abstract
A cooling system for removing heat generated by electrical components onboard aerospace vehicles flows coolant between an evaporator that removes heat from the component, and a condenser within the skin of the vehicle. The skin is formed from facesheets comprising multiple layers of polymer resin reinforced with meshes of single and double wall nanotubes. The nanotubes conduct the heat directionally so as to both distribute the heat over the skin and direct the heat to the outer surface of the skin where the heat can be carried away by air flowing over the skin. The skin may also include conductive carbon foam surrounding the condenser to reduce thermal resistance between the condenser and the facesheets.
Claims40
A composite skin for an aerospace vehicle, comprising:
- a thermal distribution system for distributing heat from a heat source laterally through the skin;
- and,
- first and second facesheets on opposite sides of the thermal distribution system, at least the first facesheet being thermally conductive for conducting heat from the distribution system to a face of the skin.
A system for controlling heat generated by electronic components on-board an airplane, comprising:
- a cooling system for absorbing heat from an electronic component and transferring the absorbed heat to a wing on the airplane;
- and,
- a thermally conductive skin on the wing connected with the cooling system for transferring the absorbed heat to air flowing over the wing.
A thermally conductive facesheet for use in the skin of an aerospace vehicle, comprising:
- a first layer of thermally conductive material for conducting heat in a first direction laterally through the skin, and,
- a second layer of thermally conductive material contacting the first layer for conducting heat in a second direction transverse to the first direction.
A method of cooling an electronic component on-board an aircraft, comprising the steps of:
- (A) transferring heat from an electronic component to a coolant;
- (B) flowing the coolant through at least a section of a wing on the aircraft;
- and,
- (C) transferring heat in the coolant to a surface of the wing.
Dependencies are inferred from the claim text.